A method for calculating the detailed hover performance of any arbitrary circulation control rotor is presented. The method includes such higher order effects as non-uniform inflow, internal ducting losses and experimental airfoil data. Calculations were performed on an untwisted constant chord blade with varying section thickness and camber. Hover Figures of Merit exceeding 0.80 are calculated for this rotor at thrust coefficient to solidity ratios of 0.20. The optimum pitch angle is determined for each thrust coefficient. The effects of slot height and tip Mach number are also analyzed. A comparison is made with a conventional rotor system of the same solidity.